阅读说明：本技术 用于涡轮喷嘴上的带特征的接头和制造 (The connector with feature and manufacture on turbine nozzle ) 是由 萨拉·萨克斯顿·安德伍德 道格拉斯·格伦·德切萨雷 迈克尔·雷·蒂尔特切尔 丹尼尔·格尼·邓恩 于 2019-05-20 设计创作，主要内容包括：用于涡轮喷嘴上的带特征的接头和制造。一种陶瓷基质复合物(CMC)部件,包括子部件,例如带流路,承载壁和壁支撑件,每个子部件由陶瓷基质复合物(CMC)组成,陶瓷基质复合物包括嵌入基质中的增强纤维。CMC部件还包括至少一个机械接头,该机械接头连接子部件,承载壁和壁支撑件以形成CMC部件。承载壁的增强纤维实质上垂直于子部件和壁支撑件的增强纤维取向。还提供了用于连接子部件,承载壁和壁支撑件以形成机械接头的方法。(The connector with feature and manufacture on turbine nozzle.A kind of ceramic matrix composite (CMC) component, including subassembly, such as band flow path, bearing wall and wall supporting element, each subassembly are made of ceramic matrix composite (CMC), and ceramic matrix composite includes the reinforcing fiber being embedded in matrix.CMC component further includes at least one mechanical splice, which connects subassembly, and bearing wall and wall supporting element are to form CMC component.The reinforcing fiber of bearing wall is orientated substantially perpendicular to the reinforcing fiber of subassembly and wall supporting element.It additionally provides for connecting subassembly, the method for bearing wall and wall supporting element to form mechanical splice.)

1. a kind of ceramic matrix composite (CMC) component (60,80,90,100,105,110,115,120,125,130,135, 140,145,150,155) characterized by comprising

Subassembly (64), the subassembly is by the ceramic matrix composite (CMC) including the reinforcing fiber (84) in insertion matrix Composition；

Bearing wall (68), the bearing wall (68) is by the ceramic matrix composite including the reinforcing fiber (84) in insertion matrix (CMC) it forms；

Wall supporting element (72,86), the wall supporting element are compound by the ceramic substrate including the reinforcing fiber (84) in insertion matrix Object (CMC) composition；With

At least one connector (78), described at least one connector connect the subassembly (64), the bearing wall (68) and described Wall supporting element (72),

Wherein the reinforcing fiber (84) of the bearing wall (68) is substantially perpendicular to the subassembly (64) and the wall branch The reinforcing fiber (84) of support member (72) is oriented.

2. component (80,100) according to claim 1, which is characterized in that wherein the wall supporting element (72) be with it is described Subassembly (64) integrally formed one.

3. component according to claim 1 (85,90,95,105,110,115,120,125,130,135,140,145, 150,155), which is characterized in that wherein the wall supporting element (86) separates and different from the subassembly (64).

4. component (115,120,125,130) according to claim 1, which is characterized in that at least one connects described in wherein Head (78) is interlocking joint (78), and the interlocking joint (78) includes at least one lug (118), at least one described lug quilt Be limited in the wall supporting element (86) and at least one corresponding recess portion (122) for being formed in the bearing wall (68) It is matingly engaged.

5. component (135) according to claim 1, which is characterized in that wherein the bearing wall (68) is configured to dovetail Shape bearing wall (136).

6. component (140,145) according to claim 1, which is characterized in that wherein the bearing wall (68) is configured to Wedge-shaped bearing wall (142).

7. component (95,110,140,145,150) according to claim 1, which is characterized in that further comprise secondary wall Supporting element (96).

8. component (150) according to claim 7, which is characterized in that wherein at least one described connector (78) is interlocking Connector, the interlocking joint include at least one lug (154), at least one described lug is limited at the secondary wall support It is matingly engaged in part (96) and at least one the corresponding recess portion (156) being formed in the bearing wall (68).

9. component (155) according to claim 1, which is characterized in that wherein at least one described connector (78) is interlocking Connector, the interlocking joint include at least one ceramic matrix composite (CMC) pin (160), and each pin is arranged on institute It states in the slot (162) in bearing wall (68) and matched engages.

10. a part of one kind for the nozzle (60) of gas turbine (10) characterized by comprising

Band (62), the band include:

Band flow path (64), it is described with flow path by include insertion matrix in reinforcing fiber (84) ceramic matrix composite (CMC) Composition, the band flow path (64) have opening (66) defined therein；

Bearing wall (68), the bearing wall is by the ceramic matrix composite (CMC) including the reinforcing fiber (84) in insertion matrix Composition；

Wall supporting element (72), the wall supporting element is by the ceramic matrix composite including the reinforcing fiber (84) in insertion matrix (CMC) it forms；With

At least one connector (78), described at least one connector connect the band flow path (64), the bearing wall (68) and described Wall supporting element (72), with formed CMC component (60,80,90,100,105,110,115,120,125,130,135,140,145, 150,155) a part,

Wherein, the reinforcing fiber (84) of the bearing wall (68) is substantially perpendicular to the band flow path (64) and the wall branch The reinforcing fiber (84) of support member (72) is oriented.

Technical field

Subject matter disclosed herein is related to ceramic matrix composite (CMC) component and forms the CMC subassembly of this component Connection.More particularly it relates to which a part of CMC nozzle and the one or more interlocked mechanical connectors of utilization are by multiple sub-portions The method of part formation CMC nozzle.

Background technique

Gas-turbine unit has multiple components.Air enters engine and passes through compressor.Compressed air passes through one A or multiple burners.In burner is one or more nozzles, is used to introduce the fuel into the air by burner In stream.Generated fuel-air mixture is lighted by igniter in the burner, to generate about 1100 DEG C to 2000 DEG C ranges The pressurized combustion gases of interior heat.This high-energy air-flow for leaving burner changes direction to downstream by first order turbine nozzle High pressure and low-pressure turbine stage.The turbine portion of gas-turbine unit includes armature spindle and one or more stage of turbines, each Stage of turbine had installation or the turbine disk (or rotor) otherwise carried by bearing and the periphery for being installed to disk and from the week of disk While the turbo blade radially extended.Turbine assembly usually passes through the high-energy that extension is generated by the burning of fuel-air mixture Air-flow generates rotary shaft power.Gas turbine scraper bowl or blade usually have air foil shape, are designed to flow path gas The thermal energy and kinetic energy of body are converted into the mechanical rotation of rotor.In these stages, the hot gas of expansion applies on turbo blade Power, so that additional rotating energy is provided, for example, driving generates the generator of electric power.

In advanced gas path (AGP) design of heat transfer for gas-turbine unit, the high temperature capabilities of CMC make its at For a kind of attractive material, it is possible thereby to such as turbo blade is manufactured, the bow-shaped part of nozzle and shield.In propeller for turboprop In machine, nozzle includes multiple blades, also referred to as blade or aerofoil profile, and each blade or multiple blades are connected to multiple bands, also referred to as Platform.

Turbine engine components are manufactured using many technologies, such as use the turbo blade of CMC, nozzle or shield Cover.CMC material generally includes the ceramic fibre reinforced material in insertion ceramic matrix material.In the case where matrix break, increase Strong material is used as the carrying component of CMC；Ceramic substrate protects reinforcing material, keeps the orientation of its fiber, and broken in no matrix Bearing load in the case where splitting.High temperature application (such as in gas-turbine unit) is it is particularly interesting that silicon substrate composite wood Material.Material of the CMC material based on silicon carbide (SiC) as certain components of gas-turbine unit, such as whirlpool are proposed Impeller blade, wheel blade, combustor liner, nozzle and shield.SiC fiber has been used as the reinforcing material of various ceramic matrix materials, Including SiC, C and Al₂O₃.Known various methods are for manufacturing the CMC component based on SiC, including Silicomp, melt infiltration (MI), chemical vapor infiltration (CVI) and polymer penetration and pyrolysis (PIP).In addition to the CMC (such as SiC) based on non-oxidized substance Except, there is also the CMC based on oxide.Although these manufacturing technologies are dramatically different each other, it is each directed to prefabricated component Manufacture and densification, by including producing component in the processing that various processing stages apply heat and/or pressure.In many feelings Under condition, complicated composite component, such as manufacture CMC gas turbine nozzle are manufactured, is related to forming fiber in minor radius, this may Lead to the challenge of manufacturability.More complicated geometry may need complicated processing, complicated compacting etc..

It is especially envisaged that carrying CMC component, such as turbine nozzle band herein, focuses on the load road of CMC component Installation supporting element on diameter supporting element and holding feature, such as turbine nozzle band wall.These features usually require the specific of fiber Orientation.More specifically, it is desirable to by the fiber alignment in load-bearing surface at perpendicular to main load path, to provide enough abrasions circle Face.The certain methods for constructing these features may relate to the curved fiber around tight corner (such as minor radius), as previously mentioned, this It may cause the challenge in terms of manufacturability.

Therefore, it is necessary to a kind of improved carrying CMC components, such as turbine nozzle band, and this carrying CMC component of manufacture Method.Obtained carrying CMC component, more specifically, included load path supporting element and holding feature, provide easily In manufacture, while keeping the intensity and toughness of entire CMC structure.

Summary of the invention

The various embodiments of the disclosure include carrying ceramic complexes (CMC) structure and manufacturing method.According to an example Property embodiment, discloses a kind of CMC component for gas turbine.CMC component includes subassembly, bearing wall and wall supporting element. Subassembly, each of bearing wall and wall supporting element are made of ceramic matrix composite (CMC), and ceramic matrix composite includes The reinforcing fiber being embedded in matrix.CMC component further includes at least one connector, connects subassembly, bearing wall and wall supporting element. The reinforcing fiber of bearing wall is orientated substantially perpendicular to the reinforcing fiber of subassembly and wall supporting element.

According to another exemplary embodiment, a kind of a part of nozzle for gas turbine is disclosed.The portion of nozzle Divide includes band flow path, bearing wall and wall supporting element.Band flow path, each of bearing wall and wall supporting element are compound by ceramic substrate Object (CMC) composition, ceramic matrix composite include the reinforcing fiber being embedded in matrix.Band flow path has defined therein open Mouthful.At least one connector connecting band flow path, bearing wall and wall supporting element are to form a part of CMC component.The enhancing of bearing wall Fiber is orientated substantially perpendicular to the reinforcing fiber of flow path and wall supporting element.

According to another exemplary embodiment, a kind of method for forming ceramic matrix composite (CMC) component is disclosed.It should Method includes: the subassembly for providing and being made of ceramic matrix composite (CMC), which includes in insertion matrix Reinforcing fiber；The bearing wall being made of ceramic matrix composite (CMC) is provided, ceramic matrix composite includes in insertion matrix Reinforcing fiber；And the wall supporting element being made of ceramic matrix composite (CMC) is provided, ceramic matrix composite includes insertion Reinforcing fiber in matrix.This method further includes mechanically connected subassembly, and bearing wall and wall supporting element are to form CMC component A part simultaneously forms at least one mechanical splice.Increasing of the reinforcing fiber of bearing wall substantially perpendicular to subassembly and wall supporting element Strong fiber orientation.

Described in detail below and appended claims are read by reference to attached drawing, the other objects and advantages of the disclosure will become It obtains obviously.Combine several attached drawings and appended claims read it is described in detail below after, the application these and other Feature and improvement will become obvious those of ordinary skill in the art.

Detailed description of the invention

By below in conjunction with description the disclosure various embodiments attached drawing various aspects of the disclosure detailed description, These and other features of the disclosure will be better understood, in which:

Fig. 1 is the cross section according to the aero gas turbine engine of one or more embodiments shown or described herein Diagram；

Fig. 2 be according to a part of the load bearing component of one or more embodiments shown or described herein, more specifically, A part of gas turbine nozzle band, schematic perspective view；

Fig. 3 is the implementation for showing a part of the load bearing component according to one or more embodiments shown or described herein The schematic cross sectional views of example；

Fig. 4 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of embodiment；

Fig. 5 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of embodiment；

Fig. 6 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of embodiment；

Fig. 7 be show the load bearing component of one or more embodiments according to shown and described herein a part it is another The schematic cross sectional views of embodiment；

Fig. 8 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of embodiment；

Fig. 9 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of embodiment；

Figure 10 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 11 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 12 is according to the schematic equidistant of the embodiment of Figure 10 of one or more embodiments shown or described herein View；

Figure 13 is another implementation according to the bearing wall with lug of one or more embodiments shown or described herein The schematic isometric view of example；

Figure 14 is another implementation according to the bearing wall with lug of one or more embodiments shown or described herein The schematic isometric view of example；

Figure 15 is according to the schematic equidistant of the embodiment of Figure 11 of one or more embodiments shown or described herein View；

Figure 16 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 17 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 18 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 19 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 20 be show the load bearing component according to one or more embodiments shown or described herein a part it is another The schematic cross sectional views of one embodiment；

Figure 21 is sold according to the CMC of the embodiment for Figure 20 of one or more embodiments shown or described herein Simplify perspective view；

Figure 22 is sold according to the CMC of the embodiment for Figure 20 of one or more embodiments shown or described herein The simplification perspective view of another embodiment；With

Figure 23, which is shown, is used to form the more of connection nozzle according to one or more embodiments shown or described herein The flow chart of the method for the interlocked mechanical connector of a subassembly.

Unless otherwise noted, otherwise attached drawing provided herein is intended to show that the feature of embodiment of the disclosure.It is believed that these Feature is suitable for the various systems including one or more other embodiments of the present disclosure.Therefore, attached drawing is not meant to include ability Domain those of ordinary skill is known for practicing all traditional characteristics of embodiment disclosed herein.

It should be noted that drawings presented here is not drawn necessarily to scale.Attached drawing is intended to only describe the allusion quotation of disclosed embodiment In terms of type, therefore it should not be considered as limiting the scope of the disclosure.In the accompanying drawings, it is identically numbered the identical member indicated between attached drawing Part.

Specific embodiment

Now with detailed reference to the embodiment of the present invention, one or more example is shown in the accompanying drawings.Each reality is provided It applies example and is to explain the present invention, rather than limit the present invention.In fact, it will be apparent to those skilled in the art that It is that without departing from the scope or spirit of the invention, can carry out various modifications and change in the present invention.For example, The feature that a part as one embodiment shows or describes can be used together with another embodiment, to generate another Embodiment.Therefore, the present invention is directed to cover these modifications and variations come within the scope of the appended claims and their.

Term used herein is used only for the purpose of describing specific embodiments, it is no intended to limit the disclosure.Such as institute here It uses, singular " one ", "one" and "the" are intended to also include plural form, unless the context is clearly stated.It will It further understands, when used in this manual, term " includes " and/or "comprising" specify the feature, integer, step, Operation, the presence of element and/or component, but do not preclude the presence or addition of other one or more features, integer, step, behaviour Make, element, component and/or combination thereof.

The approximating language used in the specification and claims is used to modify the quantificational expression of any permissible variation, Variation without will lead to relative basic function.Unless otherwise stated, as used herein approximating language, example Such as " substantially ", " substantial " and " about " indicates that the term so modified can be only applicable to degree of approximation, such as the common skill in this field As art personnel will be recognized, rather than absolute or perfect degree.Therefore, it is not limited to by the value that the term is modified specified Exact value.In at least some cases, approximating language can correspond to the precision of the instrument for measured value.Herein and entirely In description and claims, scope limitation is combined and exchanges.Unless context or language are otherwise noted, otherwise these ranges It is identified and including all subranges wherein included.

In addition, unless otherwise stated, term " first ", " second " etc. is used only as marking herein, and not purport It is required to the sequence of project application involved in these terms, position or classification.In addition, for example, reference to " second " project Do not require or exclude the project of the project or " third " or higher number in the presence of such as " first " or lower number.

As used herein, ceramic matrix composite or " CMC " refer to include answering for the ceramic substrate enhanced by ceramic fibre Close object.The some examples that can be used for the CMC of this paper may include but be not limited to matrix and reinforcing fiber (comprising oxide, carbon Compound, nitride, oxycarbide, nitrogen oxides and its mixture) material.The example of non-oxidic material includes but is not limited to (when being made up of performing silicon melt infiltration, which will be containing remaining free by CMC with carborundum substrate and silicon carbide fibre Silicon)；Silicon carbide/silicon matrix mixture and silicon carbide fibre；Nitrogenize silicon matrix and silicon carbide fibre；With silicon carbide/nitridation silicon substrate Matter mixture and silicon carbide fibre.In addition, the reinforcing fiber that CMC can have matrix and be made of oxide ceramics.Specifically, oxygen Compound-oxide CMC can the reinforcing fiber by matrix and comprising oxide-based materials form, oxide-based materials are such as oxygen Change aluminium (Al₂O₃), silica (SiO₂), alumino-silicate and their mixture.Therefore, as used herein, term " ceramics Base complex " includes but is not limited to carbon-fiber reinforced carbon (C/C), carbon fibre reinforced silicon carbide (C/SiC) and silicon carbide fibre Enhance silicon carbide (SiC/SiC).In one embodiment, compared with (non-reinforcing) bulk ceramics structure, ceramic substrate is compound Material has increased elongation, fracture toughness, thermal shock and anisotropic properties.

There is several methods that can be used for manufacturing SiC-SiC CMC.In one approach, pass through the molten of molten silicon or silicon-containing alloy Melt infiltration (MI) by base portion to be formed or fine and close chemical conversion CMC prefabricated component.In another approach, matrix is at least partly led to The chemical vapor infiltration (CVI) for crossing silicon carbide forms CMC prefabricated component.In the third method, matrix is at least partially through heat It solves silicon carbide and is formed, generate preceramic polymer.This method is commonly referred to as polymer penetration and pyrolysis (PIP).It can also make With the combination of above-mentioned three kinds of technologies.

In an example of MI CMC technique, the coat system based on boron nitride is deposited on SiC fiber.Then base is used The fiber of matter precursor material immersion coating, to form prepreg tape.A kind of method for manufacturing these bands is fiber winding.Fiber is drawn Matrix precursor slurry is crossed to bathe and the fiber of dipping is wrapped on roller.Matrix precursor can containing silicon carbide and/or carbon particulate with And organic material.It then along the fiber of the axis cutting dipping of roller, and is taken out from roller, obtains flat prepreg tape, Nominally middle fiber continues in a same direction.Resulting materials are unidirectional prepreg tapes.Continuous preimpregnation also can be used in prepreg tape Stain machine or other methods manufacture.Then shape can be cut the strip into, laying is simultaneously laminated to manufacture prefabricated component.Prefabricated component is warm Solution or burn-up, so that any organic material from matrix precursor at charcoal and generates hole.Then by the silicon infiltration of melting to more In the prefabricated component of hole, it can react to form silicon carbide with carbon there.It is desirable that excessive free silica fills any remaining hole Gap simultaneously obtains fine and close compound.The matrix produced in this way usually contains remaining free silica.

Prepreg MI technique is generated and multiple one-dimensional prepregs are stacked with two-dimensional fiber framework Material, wherein the orientation of fiber changes between layers.The orientation for being typically based on continuous fiber carrys out identification layer.Zero degree orientation is established, And based on its fiber relative to other layers of the angle design in zero degree direction.Wherein fiber is claimed perpendicular to the layer that zero direction continues For 90 degree of layers, cross-level or transverse layers.

MI method can also be used together with two dimension or 3 D weaving framework.One example of this method is slurry casting Technique, wherein fiber is woven into three-dimensional prefab or two-dimentional cloth first.In the case where cloth, by the layer cutting forming and heap of cloth It folds to form prefabricated component.Chemical vapor infiltration (CVI) technology is used to deposit interface coating (usually boron nitride-base or carbon-based) Onto fiber.CVI can also be used for depositing silicon silicon matrix layer.By the way that matrix precursor slurry to be cast in prefabricated component, then use Silicon infiltration is melted, the remainder of matrix is formed.

The alternative solution of MI method is using CVI technology one-dimensional, densifies carborundum substrate in two dimension or three-dimensional architecture. Similarly, PIP can be used for densifying the matrix of compound.The matrix that CVI and PIP is generated can be in the feelings of no excessive free silica It is generated under condition.The combination of MI, CVI and PIP can also be used for densifying matrix.

Interlocked mechanical connector as described herein can be designed with any carrying CMC structure and is used in combination, such as Heitman, B Et al. (hereinafter referred to as Heitman) submitted on July 24th, 2015 it is entitled " by ceramic matrix composite component and metal portion The U.S. of the method and system that part engages " announces those described in No.2017/0022833, and entire contents are incorporated to this Text.More specifically, wherein whole composite shape and geometry are described in the disclosure of Heitman, disclosure packet Various methods are included, including wear interface laminate vertical with loading direction, vertical with the geometry of Heitman.

Particularly, interlocked mechanical connector as described herein can be used for connecting various CMC materials, such as, but not limited to aoxidize Object-oxide CMC or SiC-SiC CMC, or CMC is connected to integral material.Interlocked mechanical connector can couple all be based on It is MI, all based on CVI, it is all based on PIP's or their combination subassembly.The interlocked mechanical connector the case where Under, may be directly joined together without subassembly or subassembly can be by silicon, silicon carbide, their combination or other Suitable material combines.Bond material can be deposited as matrix precursor material, then be densified by MI, CVI or PIP.Alternatively, Bond material can be produced by MI, CVI or PIP, without using matrix precursor in interlocked mechanical connector.In addition, this paper institute The interlocked mechanical connector stated can be formed in any appropriate stage in CMC processing.That is, subassembly can be presoaked by green Material, laminate pre-form are pyrolyzed prefabricated component, and prefabricated component densified completely or combinations thereof is constituted.

Referring now to attached drawing, wherein identical appended drawing reference corresponds to identical element always, it is first noted that Fig. 1, with Schematic form depicts the exemplary gas turbogenerator 10 being used together with aircraft, have the longitudinal direction that passes through or Axial centre bobbin thread 12 is with for reference purposes.It should be appreciated that principles described herein is equally applicable to turbofan, turbine Jet engine and turboaxle motor, and the turbogenerator for other aircraft or stationary applications.In order to provide this The concise description of a little embodiments, does not describe all features of actual implementation in the description.Although in addition, using turbine nozzle As an example, still the principle of the present invention is suitable for any low ductility channel member, it is at least partially exposed to combustion gas whirlpool It the main burning gas flow path of turbine and is formed by compound (CMC) material of ceramic substrate, more specifically, any aerofoil profile platform Shape structure, such as, but not limited to blade, tip shield etc..

Engine 10 preferably includes the core gas turbine engine usually identified by label 14 and trip disposed thereon Fan section 16.Core-engine 14 generally includes the shell 18 of generally tubular, limits annular entry 20.Shell 18 further includes Booster compressor 22, it is horizontal to first pressure for the pressure rise of air of core-engine 14 will to be entered.High-pressure multi-stage axis The forced air for carrying out automatic pressure intensifier 22 is received to flow-type compressor 24, and further increases the pressure of air.Forced air stream To burner 26, is injected fuel into burner 26 in forced air stream and increase the temperature and energy water of forced air It is flat.High-energy combustion product from burner 26 flow to the first high pressure (HP) turbine 28 for by the first HP drive shaft driving high pressure pressure Then contracting machine 24 is used to drive pressurization by the twoth LP drive shaft coaxial with the first drive shaft to the second low pressure (LP) turbine 32 Compressor 22 and fan section 16.HP turbine 28 includes HP fixed nozzle 34.LP turbine 32 includes fixed LP nozzle 35.Rotor disk Positioned at the downstream of nozzle, is rotated around the cener line 12 of engine 10 and carry the turbo blade of one group of air foil shape 36.Shield 29,38 including multiple arcs sheath section is arranged around and closely surrounds turbo blade 27,36, to limit Flow through the outer radial flow path boundary of the thermal current of turbo blade 27,36.After driving each turbine 28 and 32, combustion product Core-engine 14 is left by exhaust nozzle 40.

Fan section 16 includes rotatable axial flow fan rotor 30 and multiple fan rotor blades 46, by annular wind Fan case body 42 surrounds.It is multiple generally radially extending to should be appreciated that blower-casting 42 is passed through by core-engine 14, between circumferential direction The export orientation wheel blade 44 separated supports.In this way, blower-casting 42 surrounds fan propeller 30 and multiple fan propeller leaves Piece 46.

From the viewpoint of flowing, it should be understood that enter combustion gas by entrance 52 by the initial air stream that arrow 50 indicates Turbogenerator 10.Air stream 50 passes through fan blade 46 and is divided into mobile the first compressed air stream for passing through blower-casting 42 (being indicated by arrow 54) and the second compressed air stream (being indicated by arrow 56) for entering booster compressor 22.Second compressed air stream 56 pressure increase simultaneously enters high pressure compressor 24, as shown in arrow 58.It is being mixed with fuel and is burning it in burner 26 Afterwards, combustion product 48 leaves burner 26 and flows through the first turbine 28.Then, combustion product 48 flows through the second turbine 32 and leaves Exhaust nozzle 40, to provide thrust for gas-turbine unit 10.

Due to complicated geometry, many engine components can be made several, and be then attached to together.This A little components can also be directly subjected to hot combustion gas during the operation of engine 10, therefore there is very harsh material to want It asks.Therefore, it can more than one be manufactured and subsequent by many components of engine 10 of ceramic matrix composite (CMC) manufacture It links together.As previously mentioned, being especially envisaged that carrying CMC component, such as turbine nozzle band herein, focus on CMC Installation supporting element on the load path supporting element and holding feature, such as turbine nozzle band of component.In a preferred embodiment, more A simple geometric shape subassembly (such as flat) is used to form turbine nozzle band, such as constitutes the (figure of HP turbine nozzle 34 1).The use of multiple subassemblies allows required fiber orientation without curved fiber, while reducing manufacture complexity.

Connecting multiple CMC parts or subassembly (such as multiple turbine nozzle band subassemblies), including load path supporting element In holding feature, it is desirable to connector is formed in component process of deployment, this connector has traumatic resistance and shows toughness, Graceful failure.If connecting the interlocked mechanical joint fails of multiple CMC subassemblies, the calamity of modular construction may cause Failure.

Bonding wire, which is substantially easy to become fragile, to be especially envisaged that these connectors, this may cause the crisp of interlocked mechanical connector Property destroy.It has been established that the limitation can be by the surface area by control junction and by using simple in CMC technology Carpenter's type fittings (such as banjo fixing butt jointing, lap joint, groove joint, mortise and tenon and more elaborate sawtooth Or stepped cone connector) solved to keep the stress of junction lower.Alternatively, mechanical interlocked comprising CMC subassembly connects Head also shows graceful failure.Traditional woodworking joint, such as dovetail joggle are illustrated.Above-mentioned connector can be used for by CMC subassembly connects into two dimension or three-dimensional, such as plate and "T"-shaped.Although the connector of many carpenter's types can be in two CMC Formed mechanical interlocked between subassembly, but in order to make interlocking utilize the complete toughness of CMC, interlock feature must be oriented so as to increase Strong fiber needs to be broken so that interlocking is failed.It can be by making one on interlayer direction if interlock feature is oriented such that CMC subassembly fails to discharge interlocked mechanical connector, then interlocking toughness may be limited by the interlayer characteristic of CMC.In general, The interlaminar strength and toughness of CMC is substantially less than property in face.

Referring now to Fig. 2, to simplify a part that solid shows turbine nozzle 60 (such as nozzle 34 of Fig. 1), more Specifically a part of the load bearing component of nozzle 34.Nozzle 34 generallys include multiple blade (not shown) and multiple bands 62, Fig. 2 In illustrate only a part of single band.In the exemplary embodiment, each blade in multiple blades is between multiple bands 62 Extend and is engaged with the one or more in band 62.

It will be appreciated that though describing the nozzle for generalling include multiple blades and multiple bands in the entire disclosure, still Any kind of structure that provided description is suitable for being made of subassembly, such as, but not limited to, combustor liner, shield, Turbine central frame etc..Therefore, as described below, First CMC subassembly is not limited to band flow path.

Referring again to FIGS. 2, each of multiple bands 62 are limited by First CMC subassembly 63, First CMC subassembly 63 exists It is band flow path 64 in illustrated embodiment, with opening 66 formed therein.Opening 66 is configured to connect with wheel blade (not shown) Merge the chamber for providing cooling medium (not shown) to flow into the wheel blade being coupled, as known in the art.In multiple bands 62 Each further limited by second CMC subassembly, more specifically, being limited by bearing wall 68.As in Fig. 2 best seen from, Bearing wall 68 is essentially vertically positioned relative to band flow path 64.

In the shown embodiment, the profile on the surface 70 with flow path 64 is formed to define wall supporting element 72.Implement in substitution It in example, can be structured as with flow path 64 substantially planar (presently described), but still provide support for bearing wall 68.Again In one embodiment, wall supporting element 72 can be defined as independent and different CMC component (presently described), not with flow path 64 is integrally formed, is still configured to provide support for bearing wall 68.

As shown, being configured to include suspension part 74 with flow path 64, the holding that suspension part 74 can provide bearing wall 68 is (current Description) and/or other auxiliary to provide additional support (current description) to bearing wall 68.During operation, applied Bearing load (i.e. mechanical or pneumatic) 76 is applied on bearing wall 68 as shown in the figure.

Referring now to Fig. 3-20, show the CMC load bearing component including multiple CMC subassemblies a part (more specifically, A part of nozzle tape) multiple embodiments, be that the bearing load for the fiber plane for being approximately perpendicular to subassembly is (i.e. mechanical Or pneumatic) offer interlocked mechanical connector.

It should be understood that a part of nozzle is illustrated only, more specifically, showing single band in entire embodiment A part.As shown, each figure is portrayed as with simplified block geometry, and it is shown as the linear of the layer in component Direction is denoted as linear filling line.However, the fiber in each layer can be in any direction in the plane limited by filling line Orientation, the outer projection such as in the page.In each embodiment disclosed herein, described interlocked mechanical connector can be used for connecting Band flow path 64, bearing wall 68 and wall supporting element 72, either global feature or individually discrete subassembly are bigger to be formed Or modular construction (such as nozzle 34 of Fig. 1) a part.In alternative embodiments, any one of 62 subassembly of band can To include for bulk ceramics subassembly.

Referring more specifically to Fig. 3, the embodiment of a part of band 80 is shown comprising connect at interlocked mechanical connector 78 The multiple CMC subassemblies connect, as described herein.More specifically, in this particular example, 80 subassembly of band includes band flow path 64 With bearing wall 68.Supporting part 68, which is arranged in, to be formed in in the recess portion 82 in flow path 64.In such configuration, suspension part 74 is carrying Lotus side is that bearing wall 68 provides additional support.As in the embodiment of fig. 2, the surface 70 with flow path 64 is with confining wall branch The mode of support member 72 forms.In embodiment, the setting of bearing wall 68 enters depth d in band flow path₁。

Each of band flow path 64 including wall supporting element 72 and bearing wall 68 is engaged to be formed with being configured to mate to Interlocked mechanical connector 78.As used herein, term " engagement " and " sliding engagement " include interlocking subassembly consolidating relative to each other The insertion of fixed or on-fixed.

In the fig. 3 embodiment, with flow path 64 and bearing wall 68 by ceramic matrix composite (CMC) material of known type It constitutes.Particularly, CMC material include be embedded in matrix in multiple reinforcing fibers, and plurality of reinforcing fiber substantially along The length orientation of component.In alternative embodiments, with a ceramic base by known type in flow path 64 or bearing wall 68 Matter compound (CMC) material is formed, and is formed with another in flow path 64 or bearing wall 68 by bulk ceramics material.Entire In embodiment, filling line indicate include CMC band subassembly (more specifically, with flow path 64, bearing wall 68 and any other CMC Subassembly (presently described)) multiple fibrous layers 88 orientation/plane.Therefore, the assembled part of nozzle 80 may include one Or multiple CMC subassemblies can be ceramic matrix composite with one or more bulk ceramics subassemblies or all subassemblies (CMC) material.

The bulk ceramics of such as SiC are usually fragile material.The stress-strain diagram of this material is usually straight line, is worked as It is terminated when sample burst.Failure stress usually determines by the presence of defect, and since the rapid crack of critical defect increases And cause to fail.Unexpected failure is sometimes referred to as brittleness or catastrophic failure.Although the intensity of ceramics and failure strain are Defect is relied on, but strain of failing about~0.1% is not uncommon for.

In general, CMC material includes high-strength ceramic fiber type, such as by COI Ceramics, the Hi- of Inc manufacture Nicalon^TMType S.Optical fiber is embedded in ceramic mould matrix, such as the SiC or SiC containing residual free silica.It is multiple in SiC-SiC In the example for closing object, wherein the interface coating of such as boron nitride, is usually applied on fiber by SiC fiber reinforcement SiC matrix.It should Coating allows fiber to slide from unsticking in matrix and near matrix crack.The stress-of the fast fracture of SiC-SiC compound is answered Varied curve usually has initial linear elastic part, and wherein stress and strain is proportional to one another.As the load increases, final base Matter can rupture.In compound perfect in workmanship, crack will be bridged by reinforcing fiber.As the load on compound is further Increase, additional matrix crack will be formed, and these cracks will also be bridged by fiber.When matrix break, it can be to fiber Load is generated, stress-strain diagram becomes non-linear.Non-linear stress-strain behavior start commonly known as proportional limit or Matrix crack stress.Moderate loss assigns compound toughness, because they are slided from unsticking in matrix and near matrix crack. At the position for penetrating crack, fiber carries the entire load being applied on compound.Finally, load is big enough in fiber Failure, this causes compound to fail.CMC ability of bearing load after matrix cracking is commonly known as graceful failure.CMC performance Damage tolerance out keeps it more more preferable than the bulk ceramics of catastrophic failure.

CMC material be at least to a certain extent it is orthotropic, i.e., material is in the direction for being parallel to fibre length Tensile strength on (machine direction or 0 degree of direction) is better than in vertical direction the stretching in (90 degree or interlayer/penetration thickness direction) Intensity.Such as the physical property of the modulus and Poisson's ratio also difference in terms of fiber orientation.Most of compounds have along multiple directions The fiber of orientation.For example, the framework is made of the multilayer of unidirectional fibre in prepreg MI SiC-SiSiC CMC.It is a kind of normal The framework seen is made of the alternating layer of 0 degree and 90 degree fiber, assigns the toughness in fiber plane on all directions.However, this Kind hierarchy does not have the fiber continued on penetration thickness or interlayer direction.Therefore, the intensity and toughness of the compound exist Lower than intensity and toughness in the in-plane direction on interlayer direction.

When matrix crack is bridged by fiber, CMC shows the behavior and graceful failure of toughness.Here it is most concerned with In response to the load of application, the mutual lock machine formed when forming the CMC material subassembly of band part of nozzle 34 and linking together The failure of tool connector.If interlocked mechanical connector allow it in the case where not destroying fiber occur failure and separation When being loaded on direction, then brittleness, catastrophic failure may occur for the connector.Alternatively, if interlocked mechanical connector exists So that matrix crack in interlocked mechanical connector after fiber bridge joint crack direction on be loaded when, then there is interlocked mechanical A possibility that toughness of connector, damage tolerance, gracefulness failure.

As blowing shown in enlarged drawing for Fig. 3 forms the integrally-built every of band in embodiment disclosed herein (Fig. 3-20) A subassembly, including band flow path 64, bearing wall 68, any other CMC subassembly (presently described) is by 84 groups of multiple fibers At these fibers 84 are formed in the layer 88 oriented in the plane of corresponding subassembly, in order to provide changing for interlocked mechanical connector 78 Into interlocking and minimize joint fails.It is expected that fiber 84 is orientated normal to loading direction, to be optimized to load path Wear interface.CMC interlayer characteristic is lower than the face CMC internal characteristic, and edge loads wall supporting element in the case where no wall 68 72 laminate may also lead to interlayer damage or interlayer failure.The fiber 84 for being approximately perpendicular to loading direction orientation will be helpful to Load is distributed on the layer edge below wall supporting element 72, to reduce a possibility that interlayer is damaged/failed.It is supported in wall In the case where interlayer damage in part 72, fiber 84 can help prevent interlayer to fail.In the fig. 3 embodiment, as shown, Multiple fibers 84 extend from the top to the bottom in layer 84a, and pass in and out paper in layer 84b and extend.In the shown embodiment, layer 88 framework is symmetrical about the middle plane (Mp) of component.The symmetry of holding member layer 88 helps to minimize due to 0 degree and 90 Any difference and any deformation being likely to occur or stress between degree layer.Shown in 8 deck panels be shown as that there is typical frame Structure (0/90/0/90:90/0/90/0), it is symmetrical about middle plane Mp.In alternative embodiments, layer 88 about middle plane Mp not Symmetrically.In another alternate embodiment, which includes in the layer 88 being upwardly oriented different from 0 or 90 degree of side, such as +/- 45 It spends (bearing wall 68 of Figure 18), the combination of some other angles or various angles.In response to expected loading direction, such as arrow 76 Shown, the failure of interlocked mechanical connector 78 will need bearing wall 68 from pulling open (vertical direction being orientated in such as figure) with flow path 64, As shown in reaction force 77.In embodiment, multiple layers 88 with flow path 64 and bearing wall 68 are formed not connect by fiber 84, Because bridging interlocked mechanical connector 78 without fiber 84.Fiber 84 in wall supporting element 68 is perpendicular to the fiber in flowing platform 64 84 orientations, it is therefore desirable to which rupture is so that wall supporting element 68 fails under load 76.In this way, interlocked mechanical connector 78 is adding Carrying has toughness on direction.

Referring now to Figure 4 and 5, shown with simplification sectional view be respectively band 85,90 alternate embodiment comprising Duo Gezi The connection of component and subassembly is to form a part of bigger modular construction, more specifically, nozzle, such as the nozzle 34 of Fig. 1. It should be noted that illustrating only a part of band 85, each of 90 in the embodiment for showing and describing band 85,90.Scheming In 4 and 5 embodiment, bearing wall 68 is shown, band flow path 64 is connected at interlocked mechanical connector 78.With the implementation of Fig. 3 Example on the contrary, in the fig. 4 embodiment, independent and discrete wall supporting element 86 is arranged on the surface 70 with flow path 64, with along Height " the H of bearing wall 68_p" a part to bearing wall 68 provide support.Similar to the embodiment of Fig. 3, the setting of bearing wall 68 exists It is formed in in the recess portion 82 in flow path 64.In embodiment, the setting of bearing wall 68 enters depth d in band flow path 64₁.This In construction, suspension part 74 is that bearing wall 68 provides additional support in load side.Embodiment with Fig. 3 and 4 is on the contrary, Fig. 5's In embodiment, independent and discrete wall supporting element 86 is arranged in the recess portion 92 being formed in the surface with flow path 64 70, with edge Bearing wall 68 it is entire height " H_c" to bearing wall 68 provide support.In alternative embodiments, discrete wall supporting element 86 is only Partial Height along bearing wall 68 provides support to bearing wall 68.In such configuration, suspension part 74 is bearing wall in load side 68 provide additional support.

In the embodiment shown in Figure 4 and 5, band flow path 64, bearing wall 68 and discrete wall supporting element 86 are by ceramic substrate Compound (CMC) formation, ceramic matrix composite include the reinforcing fiber 84 being embedded in matrix.In alternative embodiments, band stream Road 64, at least one of bearing wall 68 or discrete wall supporting element 86 are formed as ceramic whole subassembly.As shown in Figures 4 and 5, Band flow path 64, bearing wall 68 and discrete wall supporting element 86 are shown as being connected to each other at interlocked mechanical connector 78.

In response to expected loading direction, as shown in arrow 76, the failure of the interlocked mechanical connector 78 in Fig. 4 and Fig. 5 will Bearing wall 68 is needed to pull open (on the vertical direction being such as orientated in figure), as shown in reaction force 77 from flow path 64.Implementing In example, band flow path 64 is formed, multiple layers 88 of bearing wall 68 and discrete wall supporting element 86 are not connected by fiber 84, because not having There is fiber 84 to bridge interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is substantially perpendicular to flow path 64 and discrete wall branch Fiber 84 in support 86 is orientated, therefore will need to disconnect so that bearing wall 68 fails under load 76.In this way, mutual lock machine Tool connector 78 has toughness on loading direction.

Referring now to Fig. 6, another embodiment of band 95 is shown with simplification sectional view, band 95 include multiple subassemblies and The connection of subassembly is to form a part of larger part structure, more specifically, nozzle, such as the nozzle 34 of Fig. 1.It should infuse Meaning, in the embodiment for showing and describing band 95, illustrates only a part of band 95.In the embodiment in fig 6, carrying is shown Wall 68 is connected to band flow path 64 at interlocked mechanical connector 78.With previous embodiment on the contrary, in this particular example, Band flow path 64 does not provide any direct lateral support to bearing wall 68.In this embodiment, independent and discrete wall supporting element 86 are arranged on the surface 70 with flow path 64, to provide support to bearing wall 68.In addition, in this particular example, secondary wall Supporting element 96 is located on the upper space 75 of suspension part 74.Secondary wall supporting element 96 is that bearing wall 68 provides additionally in load side Support.In the embodiment shown in fig. 6, band flow path 64, bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 It is formed by ceramic matrix composite (CMC), ceramic matrix composite includes the reinforcing fiber 84 being embedded in matrix.Implement in substitution In example, band flow path 64, bearing wall, it is whole that at least one of discrete wall supporting element 86 and secondary wall supporting element 96 are formed as ceramics Body subassembly.As shown in fig. 6, bearing wall, discrete wall supporting element 86 and secondary wall supporting element 96 are shown as mutual with flow path 64 It is connected to each other at lock mechanical splice 78.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 It is pulled open (on the vertical direction being orientated in such as figure), as shown in reaction force 77 from flow path 64.In embodiment, band stream is formed Multiple layers 88 of road 64, bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 are not connected by fiber 84, because There is no fiber 84 to bridge interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is substantially perpendicular to the fiber in flow path 64 84, discrete wall supporting element 86 and secondary wall supporting element 96 are orientated, it is therefore desirable to be disconnected so that bearing wall 68 loses under load 76 Effect.In this way, interlocked mechanical connector has toughness on loading direction.

Referring now to Fig. 7 and Fig. 8, shown with simplification sectional view be respectively labeled as 100,105 band other implementation Example comprising the connection of multiple subassemblies and subassembly is to form a part of bigger modular construction, more specifically, nozzle, example Such as the nozzle 34 of Fig. 1.Similar to previous embodiment, it should be noted that in the embodiment for showing and describing band 100,105, only Show a part of corresponding band.The embodiment of Fig. 7 is approximately similar to the previously described embodiment of Fig. 3, wherein band flow path 64 Profile be shaped to limit integral wall supporting element 72.The embodiment of Fig. 8 is approximately similar to the embodiment of Fig. 4, wherein individually and Discrete wall supporting element 86 is arranged on the surface 70 with flow path 64, to provide support to bearing wall 68.In the implementation of Fig. 7 and 8 In example, bearing wall 68 and corresponding wall supporting element 72 or 86 are shown, bearing wall 68 is connected at interlocked mechanical connector 78 Band flow path 64.With the embodiment of Fig. 3 and 4 on the contrary, the bearing wall 68 of the embodiment of Fig. 7 and 8 is without the recessed surface with flow path 64 In 70.Therefore, the band flow path 64 in Fig. 7, more specifically, integrally formed wall supporting element 72, provides directly for bearing wall 68 Lateral support, but the band flow path 64 in Fig. 8 provides any direct lateral support for bearing wall 68.In the institute of Fig. 7 and 8 In the embodiment shown, band flow path 64, bearing wall 68 and wall supporting element 72 or 86 are formed by ceramic matrix composite (CMC), ceramics Base complex includes the reinforcing fiber 84 being embedded in matrix.In alternative embodiments, band flow path 64, bearing wall 68 and wall support At least one of part 72 or 86 is formed as ceramic whole subassembly.As shown in FIG. 7 and 8, band flow path 64, bearing wall 68 and wall branch Support member 72 or 86 is shown as being connected to each other at interlocked mechanical connector 78.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 It is pulled open (on the vertical direction being orientated in entering figure), as shown in reaction force 77 from flow path 64.In embodiment, band stream is formed Road 64, bearing wall 68 and wall supporting element 72 or 86 multiple layers 88 are not connected by fiber 84, because bridging mutually without fiber 84 Lock mechanical splice 78.Fiber 84 in bearing wall 68 is substantially perpendicular to the fiber 84 in flow path 64 and wall supporting element 72 or 86 Orientation, it is therefore desirable to disconnect so that bearing wall 68 fails under load 76.In this way, interlocked mechanical connector 78 is in load side There is toughness upwards.

Referring now to Fig. 9, another embodiment of band 110 is shown with simplification sectional view, band 110 include multiple subassemblies and The connection of subassembly is to form a part of larger part structure, more specifically, nozzle, such as the nozzle 34 of Fig. 1.It should infuse Meaning, in the embodiment for showing and describing band 110, illustrates only a part of band 110.In the embodiment in fig. 9, it shows and holds Wall 68 is carried, band flow path 64 is connected at interlocked mechanical connector 78.Similar to the embodiment of Fig. 6 and 8, in the specific embodiment In, band flow path 64 does not provide any direct lateral support to bearing wall 68.In this embodiment, independent and discrete wall support Part 86 is arranged on the surface 70 with flow path 64, to provide support to bearing wall 68.With previous disclosed embodiment on the contrary, at this In specific embodiment, discrete wall supporting element 86 is substantially plane, if any, only includes minimized profile.In addition, In In the specific embodiment, secondary wall supporting element 96 is located on the upper space 75 of protruding portion 74.Secondary wall supporting element 96 is carrying Lotus side is that bearing wall 68 provides additional support.In the embodiment shown in fig. 9, band flow path 64, bearing wall 68, discrete wall branch Support member 86 and secondary wall supporting element 96 are formed by ceramic matrix composite (CMC), and ceramic matrix composite includes in insertion matrix Reinforcing fiber 84.In alternative embodiments, band flow path 64, bearing wall, discrete wall supporting element 86 and secondary wall supporting element 96 At least one of be formed as ceramic whole subassembly.As shown in figure 9, with flow path 64, bearing wall 68, discrete wall supporting element 86 It is shown as being connected to each other at interlocked mechanical connector 78 with secondary wall supporting element 96.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 It is pulled open (on the vertical direction being orientated in such as figure), as shown in reaction force 77 from flow path 64.In embodiment, band stream is formed Multiple layers 88 of road 64, bearing wall 68, wall supporting element 72 and secondary wall supporting element 96 are not connected by fiber, because without fiber Bridge interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is substantially perpendicular to the fiber 84 in flow path 64, discrete wall Supporting element 86 and secondary wall supporting element 96 are orientated, it is therefore desirable to be disconnected so that bearing wall 68 fails under load 76.With this side Formula, interlocked mechanical connector 78 have toughness on loading direction.

Referring now to Figure 10-15, show be respectively labeled as 115,120,125,130 band multiple embodiments, packet The connection of multiple subassemblies and subassembly is included to form a part of bigger modular construction, more specifically, nozzle, such as Fig. 1 Nozzle 34.Figure 10 and 12 shows embodiment respectively with simplification sectional view and the isometric view simplified.Figure 11 and 15 is respectively with letter The isometric view changing sectional view and simplifying shows another embodiment.Figure 13 and 14 is shown additional with simplified isometric view The embodiment with lug.

It is similar with the embodiment of front, it should be noted that in the embodiment for showing and describing band 115,120, to illustrate only A part of corresponding band.In each embodiment of Figure 10-15, the independent and discrete setting of wall supporting element 86 is being formed in band stream In recess portion 92 in the surface 70 on road 64, to provide support to bearing wall 68.In the embodiment of Figure 10-15, carrying is shown Wall 68 is connected to band flow path 64 and corresponding wall supporting element 86 at interlocked mechanical connector 78.Bearing wall setting is being formed in In recess portion 82 in surface 70 with flow path 64.Therefore, band flow path 64, more specifically, suspension part 74, provides directly for bearing wall 68 The lateral support connect.In alternative embodiments, the surface 70 with flow path 64 is arranged in bearing wall 68 and discrete wall supporting element 86 On, it and may include secondary wall supporting element, as previously discussed with respect to described in Fig. 6 and 9, to provide extra support to bearing wall 68.

With previous disclosed embodiment on the contrary, in the embodiment shown in Figure 10-15, bearing wall 68 and the support of discrete wall Part 86 includes the interlock feature 116 of one or more cooperation engagements, and additional interlocking dress is provided at interlocked mechanical connector 78 It sets.More specifically, in each example, discrete wall supporting element 86 includes one or more lugs 118, each lug 118 One or more recess portions 122 in bearing wall 68 are configured to and are formed in be matingly engaged.In the embodiment of Figure 10 and 12, point Vertical wall supporting element 86 includes single lug 118, and bearing wall 68 includes the single recess portion 122 of cooperation, and each recess portion extends Fundamental length " the L of bearing wall 68 and discrete wall supporting element 86₁" (Figure 12-15).It is discrete in the embodiment of Figure 11 and 15 Wall supporting element 86 includes multiple lugs 118, and bearing wall 68 includes multiple cooperating recesses 122, and each cooperating recesses 122 extend Fundamental length " the L of bearing wall 68 and discrete wall supporting element 86₁".It is the embodiment of band shown in Figure 13 and 14, marks respectively It is denoted as 125 and 130.It respectively include discrete wall supporting element 86 with 125 and 130, wall supporting element 86 includes multiple lugs 118 and holds Wall 68 is carried, bearing wall 68 includes multiple cooperating recesses 122.With Figure 10,11,12 and 15 embodiment is on the contrary, 118 He of each lug Cooperating recesses 122 only extend the partial-length of bearing wall 68 and wall supporting element 86.

Point in the illustrated embodiment of Figure 10-15, with flow path 64, bearing wall 68 and including one or more lugs 118 Vertical wall supporting element 86 is by including that the ceramic matrix composite (CMC) for the reinforcing fiber 84 being embedded in matrix is formed.It is real in substitution It applies in example, at least one in discrete wall supporting element 86 with flow path 64, bearing wall 68 and including one or more lugs 118 It is a, be formed as ceramic whole subassembly.As shown in fig. 10-15, band flow path 64, bearing wall 68 and discrete wall supporting element 86 are shown To be connected to each other at interlocked mechanical connector 78.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 It is pulled open (on the vertical direction being orientated in such as figure), as shown in reaction force 77 from flow path 64.In embodiment, band stream is formed Multiple layers 88 of road 64, bearing wall 68 and discrete wall supporting element 86 are not connected by fiber 84, because bridging without fiber 84 Interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is basically perpendicular to the fiber 84 in flow path 64 and discrete wall support 86 Orientation, it is therefore desirable to disconnect so that bearing wall 68 fails under load 76.In this way, interlocked mechanical connector 78 is in load side There is toughness upwards.

Referring now to fig. 16, another embodiment of band 135 is shown with simplification sectional view, band 135 includes multiple subassemblies Connection with subassembly is to form a part of larger part structure, more specifically, nozzle, such as the nozzle 34 of Fig. 1.It should infuse Meaning, in the embodiment for showing and describing band 135, illustrates only a part of band 135.In the embodiment of figure 16, it shows Bearing wall 68 is connected to band flow path 64 at interlocked mechanical connector 78.In the embodiment of figure 16, bearing wall 68 is shown, It is connected to flow path 64 and discrete wall supporting element 86 at interlocked mechanical connector 78.In this particular example, bearing wall 68 be swallow-tail form bearing wall 136, is configured with swallow-tail form part, which, which sets up separately, sets in recess portion 82, recess portion 82 With the geometry ordinatedly formed, it is formed in the surface 70 with flow path 64 to provide support for swallow-tail form bearing wall 136. Discrete wall supporting element 86 is shown as being formed as discrete and isolated component, is arranged in and is formed in the surface 70 with flow path 64 Recess portion 92 in, along the full height " H of swallow-tail form bearing wall 136_c" it is that swallow-tail form bearing wall 136 provides support.It is replacing For in embodiment, discrete wall supporting element 86 is that swallow-tail form bearing wall 136 mentions only along the Partial Height of swallow-tail form bearing wall 136 For support.As shown, with flow path 64, more specifically, suspension part 74 and wall supporting element are that swallow-tail form bearing wall 136 provides directly The lateral support connect.In alternative embodiments, discrete wall supporting element 86 is arranged on the surface 70 with flow path 64, and can wrap Secondary wall supporting element is included, as previously discussed with respect to described in Fig. 6 and 9, to provide extra support for swallow-tail form bearing wall 136.

In the embodiment shown in Figure 16, band flow path 64, swallow-tail form bearing wall 136 and discrete wall supporting element 86 are by ceramics Base complex (CMC) formation, ceramic matrix composite include the reinforcing fiber 84 being embedded in matrix.In alternative embodiments, Band flow path 64, at least one of swallow-tail form bearing wall 136 and discrete wall support 86 are formed as ceramic whole subassembly.Such as figure Shown in 16, band flow path 64, swallow-tail form bearing wall 136 and discrete wall supporting element 86 are shown as at interlocked mechanical connector 78 each other Connection.

As best seen from, in embodiment, swallow-tail form bearing wall 136 may include optional noodles insertion piece in Figure 16 138, entitled " composite component and its formation with T or L shape connector submitted such as Feie, B etc. on January 24th, 2018 The U.S. Patent Application Serial Number 15/878 of method ", discussed in 687, entire contents are incorporated herein.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 From being pulled open with flow path 64 (on the vertical direction being orientated in such as figure), as shown in reaction force 77.In embodiment, band is formed Multiple layers 88 of flow path 64, bearing wall 68 and discrete wall supporting element 86 are not connected by fiber 84, because without 84 bridge of fiber Connect interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is basically perpendicular to the fibre in flow path 64 and discrete wall supporting element 86 84 orientation of dimension, it is therefore desirable to disconnect in order, and/or cut the part of swallow-tail form part 136, for bearing wall 68 in load 76 Lower failure.In this way, interlocked mechanical connector 78 has toughness on loading direction.

Referring now to fig. 17 and 18, shown with simplification sectional view be respectively band 140,145 embodiment, band 140,145 wraps The connection of multiple subassemblies and subassembly is included to form a part of bigger modular construction, more specifically, nozzle, such as Fig. 1 Nozzle 34.Illustrate only a part of band 140,145.In the embodiment of Figure 17 and 18, bearing wall 68 is shown, is being interlocked It is connected at mechanical splice 78 with flow path 64 and discrete wall supporting element 86.Similar to the embodiment of Fig. 6 and 8, in the specific reality It applies in example, band flow path 64 does not provide any direct lateral support to bearing wall 68.In this embodiment, independent and discrete wall Supporting element 86 is arranged on the surface 70 with flow path 64, to provide support to bearing wall 68.In addition, in this particular example, Secondary wall supporting element 96 is located on the upper space 75 of suspension part 74.Secondary wall supporting element 96 is that bearing wall 68 mentions in load side For additional support.With previous disclosed embodiment on the contrary, bearing wall supporting element 68 is configured with wedge geometry and attached Icon note 142.In the embodiment of Figure 17, the fiber 84 in wedge-shaped bearing wall supporting element 142 is basically perpendicular to band 64 He of flow path Fiber 84 in discrete wall supporting element 86 is orientated.In the embodiment of figure 18, the fiber 84 in wedge-shaped bearing wall supporting element 142 It is not orthogonal to or is parallel to and be orientated with the fiber 84 in flow path 64 and discrete wall supporting element 86.

In the embodiment shown in Figure 17 and 18, band flow path 64, wedge-shaped bearing wall 142 and discrete wall supporting element 86 are by making pottery Porcelain base complex (CMC) formation, ceramic matrix composite include the reinforcing fiber 84 being embedded in matrix.In alternate embodiment In, band flow path 64, at least one of wedge-shaped bearing wall 142 and discrete wall supporting element 86 are formed as ceramic whole subassembly. As shown in Figure 18, band flow path 64, wedge-shaped bearing wall 142 and discrete wall supporting element 86 are shown as at interlocked mechanical connector 78 It is connected to each other.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need wedge shape carrying Wall 68 pulls open (on the vertical direction being orientated in such as figure), as shown in reaction force 77 from flow path 64.In embodiment, it is formed Multiple layers 88 with flow path 64, wedge-shaped bearing wall 68 and discrete wall supporting element 86 are not connected by fiber 84, because without fibre 84 bridge joint interlocked mechanical connector 78 of dimension.Fiber 84 in wedge-shaped bearing wall 68 is basically perpendicular to flow path 64 and discrete wall support Fiber 84 in part 86 is orientated, it is therefore desirable to be disconnected so that wedge-shaped bearing wall 68 fails under load 76.In this way, it interlocks Mechanical splice 78 has toughness on loading direction.

Referring now to fig. 19, the embodiment of band 150 is shown with simplification sectional view, band 150 includes multiple subassemblies and son The connection of component is to form a part of larger part structure, more specifically, nozzle, such as the nozzle 34 of Fig. 1.Illustrate only band 150 a part.In the embodiment of figure 19, bearing wall 68 is shown, band flow path is connected at interlocked mechanical connector 78 64, discrete wall supporting element 86 and secondary wall supporting element 96.In the embodiment of figure 19, independent and discrete wall supporting element 86 is set It sets on the surface 70 with flow path 64, to provide support to bearing wall 68.Bearing wall 68, which is arranged in, is formed in the table with flow path 64 In recess portion 82 in face 70.Therefore, discrete wall supporting element 86 is that bearing wall 68 provides direct lateral support.Band 150 also wraps Secondary wall supporting element 96 is included, as previously discussed with respect to described in Fig. 6 and 9, to be that bearing wall 68 provides additional support on load side.

With previous disclosed embodiment on the contrary, in the embodiment shown in Figure 19, bearing wall 68 and secondary wall supporting element 96 Interlock feature 152 including one or more cooperation engagements, provides additional interlock at interlocked mechanical connector 78.More Specifically, secondary wall supporting element 96 includes one or more lugs 154, and each lug 154 is configured to and is formed in bearing wall 68 In one or more recess portions 156 be matingly engaged.In the embodiment of figure 19, secondary wall supporting element 96 includes single lug 154, and bearing wall 68 includes the single recess portion 156 of cooperation, and each recess portion 156 extends bearing wall 68 and secondary wall supporting element 96 Fundamental length.In alternative embodiments, secondary wall supporting element 96 includes multiple lugs 154, and bearing wall 68 includes multiple Mating groove 156, each mating groove 156 extend the fundamental length and/or part length of bearing wall 68 and secondary wall supporting element 86 Degree, as similar with described in Figure 10-15.

In the embodiment shown in Figure 19, band flow path 64, bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 are formed by ceramic matrix composite (CMC), and ceramic matrix composite includes the reinforcing fiber 84 being embedded in matrix.It is substituting In embodiment, band flow path 64, bearing wall 68, at least one of discrete wall supporting element 86 and secondary wall supporting element 96 are formed as Ceramic entirety subassembly.As shown in figure 19, band flow path 64, bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 It is shown as being connected to each other at interlocked mechanical connector 78.

In response to expected loading direction, as shown in arrow 76, the failure of interlocked mechanical connector 78 will need bearing wall 68 It is pulled open (on the vertical direction being orientated in such as figure), as shown in reaction force 77 from flow path 64.In embodiment, band stream is formed Multiple layers 88 of road 64, bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 are not connected by fiber 84, because There is no fiber 84 to bridge interlocked mechanical connector 78.Fiber 84 in bearing wall 68 is basically perpendicular to the fiber 84 in flow path 64, Bearing wall 68, discrete wall supporting element 86 and secondary wall supporting element 96 are orientated, it is therefore desirable to be disconnected so that bearing wall 68 is in load 76 lower failures.In this way, interlocked mechanical connector 78 has toughness on loading direction.

Referring now to Fig. 20, the embodiment of band 155 is shown with simplification sectional view, band 155 includes multiple subassemblies and son The connection of component is to form a part of larger part structure, more specifically, nozzle, such as the nozzle 34 of Fig. 1.Illustrate only band 155 a part.In the embodiment of figure 20, bearing wall 68 is shown, band flow path is connected at interlocked mechanical connector 78 64 and discrete wall supporting element 86.In the embodiment of figure 20, independent and discrete wall supporting element 86 is arranged in flow path 64 In recess portion 92, to provide support to bearing wall 68.The recess portion 82 being formed in the surface with flow path 64 70 is arranged in bearing wall 68 In.Therefore, discrete wall supporting element 86 is that bearing wall 68 provides direct lateral support.In alternative embodiments, band 155 also wraps Secondary wall supporting element is included, as previously discussed with respect to described in Fig. 6 and 9, to provide additional support as bearing wall 68 in load side.

With previous disclosed embodiment on the contrary, in the embodiment shown in Figure 20, bearing wall 68 is matched including one or more The interlock feature that splice grafting closes, provides additional interlock at interlocked mechanical connector 78.In the embodiment of figure 20, it interlocks Mechanical splice 78 includes at least one other interlocking subassembly 158 comprising at least one interlocking CMC pin 160, each interlocking CMC pin 160 sets within it, to be matingly engaged with one at least one receiving slit 162 for being formed in bearing wall 68, And in one at least one recess portion 156 formed in discrete wall supporting element 86, to be interlocked mechanical connector 78 Additional intensity is provided.

At least one interlocking CMC pin 160 is generally similar to " cake " in wooden joiner field.In the embodiment of Figure 20 In, the single length for interlocking CMC pin 160 and extending bearing wall 68.In alternative embodiments, it can be sold in conjunction with multiple interlocking CMC 160, each pin only extends the partial-length of bearing wall.In the embodiment of figure 20, interlocking CMC pin 160 can be from the outer of band 155 Portion is inserted into the receiving slit 162 of cooperation.In embodiment, when using the matrix of such as glue, at least one interlocking CMC pin 160, the receiving slit 162 and recess portion 156 of cooperation are not needed configured with close tolerance.In alternative embodiments, at least one is interlocked CMC pin 160, the receiving slit 162 and recess portion 156 of cooperation are configured with close tolerance.

In the shown embodiment, it interlocks each of CMC pin 160 and is configured to the shape with substantial rectangular, such as In Figure 21 best seen from, or substantially cylindrical shape, as in Figure 22 best seen from.In alternative embodiments, at least One interlocking CMC pin 160 can have any geometry, including but not limited to oval, round, trapezoidal etc..Multiple interlocking CMC One in pin 160 is arranged in the receiving slit 162 of cooperation, to engage bearing wall in a manner of forming interlocked mechanical connector 78 68。

Figure 23 is the method according to a part of formation ceramic matrix composite (CMC) nozzle of embodiment disclosed herein 200 flow chart.As shown in figure 23, method 200 includes providing to be made of ceramic matrix composite (CMC) in step 202 Multiple band subassemblies, ceramic matrix composite include the reinforcing fiber being embedded in matrix.As previously mentioned, multiple reinforcing fibers along The length orientation of subassembly.

Next, in step 204, subassembly is mechanically connected to each other in interlocked mechanical joint, to form nozzle A part.It may include at least one interlocked mechanical connector according to any previous embodiment.Subassembly so that bearing wall enhancing The mode that fiber is essentially vertically orientated with the reinforcing fiber with flow path is connected with each other.Interlocked mechanical connector was manufactured in CMC With high pressure sterilization (AC) state, the formation of one of after-flame (BO) state or melt infiltration (MI) state in journey.In embodiment, it interlocks Mechanical splice may include being directly joined together component or component can be by silicon, silicon carbide, their combination or its He combines suitable material.Bond material can be deposited as matrix precursor material, then be densified by MI, CVI or PIP.Or Person, bond material can be produced by MI, CVI or PIP, without using matrix precursor in interlocked mechanical connector.As previously mentioned, Interlocked mechanical connector as described herein can be formed in any appropriate stage of CMC processing.That is, interlocking subassembly can be by Green prepreg, laminate pre-form are pyrolyzed prefabricated component, and prefabricated component densified completely or combinations thereof is constituted.

Therefore, it describes using interlocked mechanical connector and connects multiple subassemblies, more specifically, being connect using interlocked mechanical Head, including one or more lugs, protrusion, recess portion reinforce CMC pin, including subassembly or the ceramic fibre of interlock It needs to be disconnected, to separate interlocked mechanical connector on expected loading direction.Although some existing interlocked mechanical connectors It works in this way, but others will not and may be failed and shearing interlock feature on interlayer direction.Such as Interlocked mechanical connector as described herein provides the reinforcement for constituting the subassembly of interlocked mechanical connector, connects without enhancing interlocked mechanical Head itself.This method can greatly simplify manufacturing process and prevent the property that may occur on the direction orthogonal with reinforcement from damaging It loses.The interlocked mechanical connection of subassembly as described herein can laying state before being laminated, in the height of CMC manufacturing process Pressure sterilizing (AC) burns out in (BO) or melt infiltration (MI) state or combinations thereof and completes.For the connector manufactured under MI state, Interlocked mechanical connector may leave " degumming ".These connectors may also be easier to repair.In embodiment, such as plate etc Simple shape can be (under the high pressure sterilization state) of green processing and use carpenter's type interlock machine as described herein The assembling of tool connector.In embodiment, CMC substrate precursor slurry (or its variant) can be used for that CMC subassembly is combined or is glued at Together.Final densification and combination occurs in MI state.

Although describing the present invention according to one or more specific embodiments, but it is clear that those skilled in the art can To use other forms.It should be appreciated that in methods illustrated and described herein other mistakes can be performed simultaneously unshowned Journey, and the sequence of process can be rearranged according to various embodiments.Furthermore it is possible to the process described in one or more Between execute pilot process.The process flow being illustrated and described herein is not necessarily to be construed as the limitation to various embodiments.

This written description uses examples to disclose the disclosure, including optimal mode, and also enables those skilled in the art The disclosure is enough practiced, the method including manufacturing and using any device or system and executing any combination.The disclosure can be special Sharp range is defined by the claims, and may include other examples that those skilled in the art expect.If these other show Example has the structural detail not different from the literal language of claim, or if they include literal with claim Equivalent structural elements of the language without essential difference, then these other examples are intended within the scope of the claims.

Various features of the invention, aspect and advantage can also be embodied in various technical solutions described in following item item In, these schemes can combine in any combination:

1. a kind of ceramic matrix composite (CMC) component characterized by comprising

Subassembly, the subassembly is by including that the ceramic matrix composite (CMC) for the reinforcing fiber being embedded in matrix forms；

Bearing wall, the bearing wall is by including that the ceramic matrix composite (CMC) for the reinforcing fiber being embedded in matrix forms；

Wall supporting element, the wall supporting element is by the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix Composition；With

At least one connector, at least one described connector connect the subassembly, the bearing wall and the wall supporting element,

Wherein institute of the reinforcing fiber of the bearing wall substantially perpendicular to the subassembly and the wall supporting element Reinforcing fiber is stated to be oriented.

2. according to component described in item item 1, which is characterized in that wherein the wall supporting element and the subassembly entirety shape At.

3. according to component described in item item 1, which is characterized in that wherein the wall supporting element separates and not with the subassembly Together.

4. according to component described in item item 1, which is characterized in that wherein at least one described connector is interlocking joint, described Interlocking joint includes at least one lug, at least one described lug be limited in the wall supporting element and be formed in institute It engages with stating at least one corresponding recesses fit in bearing wall.

5. according to component described in item item 1, which is characterized in that wherein the bearing wall is configured to swallow-tail form bearing wall.

6. according to component described in item item 1, which is characterized in that wherein the bearing wall is configured to wedge-shaped bearing wall.

7. according to component described in item item 6, which is characterized in that wherein the reinforcing fiber of the wedge-shaped bearing wall is vertical The reinforcing fiber in the subassembly and the wall supporting element is oriented.

8. according to component described in item item 1, which is characterized in that further comprise secondary wall supporting element.

9. according to component described in item item 8, which is characterized in that wherein at least one described connector is interlocking joint, described Interlocking joint includes at least one lug, at least one described lug be limited in the secondary wall supporting element and with formation Engage at least one corresponding recesses fit in the bearing wall.

10. according to component described in item item 1, which is characterized in that wherein at least one described connector is interlocking joint, described Interlocking joint includes at least one ceramic matrix composite (CMC) pin, and each pin is arranged on the slot in the bearing wall In and matched engage.

11. according to component described in item item 1, which is characterized in that wherein the bearing wall, which is arranged on, is formed in the son In recess portion in the upper space of component.

12. according to component described in item item 11, which is characterized in that wherein the wall supporting element be arranged on be formed in it is described In the recess portion in the upper space of subassembly.

13. according to component described in item item 11, which is characterized in that wherein the wall supporting element is arranged on the subassembly The upper space on.

14. according to component described in item item 1, which is characterized in that wherein the bearing wall is arranged on the subassembly On upper space.

15. according to component described in item item 14, which is characterized in that wherein the wall supporting element is arranged on the subassembly The upper space on.

16. according to component described in item item 1, which is characterized in that wherein the CMC component is combustion turbine engine components In nozzle a part.

17. a kind of a part of the nozzle for gas turbine characterized by comprising

Band, the band include:

Band flow path, it is described to be made of with flow path the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix, The band flow path has opening defined therein；

Bearing wall, the bearing wall is by including that the ceramic matrix composite (CMC) for the reinforcing fiber being embedded in matrix forms；

Wall supporting element, the wall supporting element is by the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix Composition；With

At least one connector, at least one described connector connect the band flow path, the bearing wall and the wall supporting element, To form a part of CMC component,

Wherein, the reinforcing fiber of the bearing wall is substantially perpendicular to the institute with flow path and the wall supporting element Reinforcing fiber is stated to be oriented.

18. according to nozzle described in item item 17, which is characterized in that wherein at least one described connector is interlocking joint, institute Stating interlocking joint includes one or more lugs, and one or more of lugs are limited in the wall supporting element, and with Engage to the corresponding one or more recesses fits being formed in the bearing wall.

19. according to nozzle described in item item 17, which is characterized in that further comprise secondary wall supporting element.

20. according to nozzle described in item item 19, which is characterized in that wherein at least one described connector is interlocking joint, institute Stating interlocking joint includes one or more lugs, and one or more of lugs are limited in the secondary wall supporting element, and And it is engaged with corresponding one or more recesses fits for being formed in the bearing wall.

21. according to nozzle described in item item 17, which is characterized in that wherein at least one described connector is interlocking joint, institute Stating interlocking joint includes swallow-tail form bearing wall, and the swallow-tail form bearing wall is matched with the corresponding recess portion in flow path is formed in Close ground engagement.

22. according to nozzle described in item item 17, which is characterized in that wherein at least one described interlocking joint is held including wedge shape Carry wall.

23. according to nozzle described in item item 17, which is characterized in that wherein at least one described connector is interlocking joint, institute Stating interlocking joint includes at least one ceramic matrix composite (CMC) pin, and each pin is arranged in the bearing wall In slot and matched engage.

24. a kind of method for forming ceramic matrix composite (CMC) component, which is characterized in that the described method includes:

The subassembly being made of the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix is provided；

The bearing wall being made of the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix is provided；

The wall supporting element being made of the ceramic matrix composite (CMC) including the reinforcing fiber in insertion matrix is provided；With

The mechanically connected subassembly, the bearing wall and the wall supporting element, to form a part of CMC component simultaneously At least one mechanical splice is formed,

Wherein institute of the reinforcing fiber of the bearing wall substantially perpendicular to the subassembly and the wall supporting element Reinforcing fiber is stated to be oriented.